Stackable pancake satellite

1. An apparatus, comprising:

at least one satellite having a plurality of sections that are attached to each other, wherein the plurality of sections are folded or rotated together prior to launch, and the plurality of sections are unfolded or rotated away from each other when deployed upon reaching orbit;

a first one of the plurality of sections is a satellite body that includes at least one antenna;

a second one of the plurality of sections includes at least one solar panel attached to the satellite body for converting light from the Sun to electricity; and

a third one of the plurality of sections includes at least one splash plate reflector attached to the satellite body for reflecting radio frequency signals between Earth and the at least one antenna;

when deployed, the at least one solar panel is rotated away from the satellite body to point towards the Sun, and the at least one splash plate reflector is rotated away from the satellite body to direct the radio frequency signals between the Earth and the at least one antenna.

2. The apparatus of claim 1 , wherein the satellite body has a first side that acts as a thermal radiator and a second side opposite the first side that includes the at least one antenna.

3. The apparatus of claim 2 , wherein the at least one solar is panel attached to the first side of the satellite body.

4. The apparatus of claim 2 , wherein the at least one splash plate reflector is attached to the second side of the satellite body.

5. The apparatus of claim 2 , wherein the at least one solar panel is pointed at the Sun, the at least one splash plate reflector is pointed at the Earth, and the first side of the satellite body that acts as the thermal radiator is pointed into space.

6. The apparatus of claim 2 , wherein the satellite body has a cavity on the first side and a hollow region on the second side, such that, when folded together, the at least one solar panel is folded and stowed within the hollow region, the at least one antenna is disposed within the cavity, and the at least one splash plate reflector is stored adjacent to the at least one antenna in the cavity.

7. The apparatus of claim 6 , further comprising:

a polygonal closeout member covers the first side of the satellite body surrounding the cavity; and

the first side of the satellite body that acts as the thermal radiator and the at least one solar panel are disposed within the hollow region, and the at least one solar panel comprises a plurality of foldable solar arrays that, when folded, are enclosed within the hollow region.

8. The apparatus of claim 6 , wherein the at least one solar panel includes a plurality of panel elements having substantially the same shape, and the plurality of panel elements are each folded upon each other to fit within the hollow region.

9. The apparatus of claim 2 , wherein the first one of the plurality of sections includes bus and payload units mounted on or with the first side of the satellite body that acts as the thermal radiator.

10. The apparatus of claim 1 , wherein the at least one solar panel comprises two or more solar panels.

11. The apparatus of claim 1 , wherein the at least one solar panel comprises a multi-segmented array that is configured to be at least partially folded onto itself.

12. The apparatus of claim 1 , wherein the at least one antenna comprises a multi-beam antenna.

13. The apparatus of claim 1 , wherein at least one thruster is attached to the satellite body to maintain orbit phasing.

14. The apparatus of claim 1 , wherein a periphery outline of the plurality of sections, when folded together, is oval, elliptical, round or polygonal in shape.

15. The apparatus of claim 1 , wherein the plurality of sections, when folded together, maintain a substantially flat profile.

16. The apparatus of claim 1 , wherein the at least one satellite comprises a plurality of satellites configured for being stacked within a payload fairing of a launch vehicle.

17. The apparatus of claim 16 , wherein the plurality of satellites are disposed within the payload fairing of the launch vehicle in a stacked column configuration prior to launch.

18. The apparatus of claim 16 , wherein the plurality of satellites comprises at least one top satellite disposed vertically on top of at least one bottom satellite within the payload fairing of the launch vehicle, and each bottom satellite includes a plurality of corner fittings that bear launch loads for the bottom satellite and the at least one top satellite.

19. The apparatus of claim 16 , wherein the plurality of satellites are passively dispensed from the payload fairing of the launch vehicle upon reaching orbit.

20. A method, comprising:

fabricating at least one satellite having a plurality of sections that are attached to each other, wherein the plurality of sections are folded or rotated together prior to launch, and the plurality of sections are unfolded or rotated away from each other when deployed upon reaching orbit;

a first one of the plurality of sections is a satellite body that includes at least one antenna;

a second one of the plurality of sections includes at least one solar panel attached to the satellite body for converting light from the Sun to electricity; and

a third one of the plurality of sections includes at least one splash plate reflector attached to the satellite body for reflecting radio frequency signals between Earth and the at least one antenna;

when deployed, the at least one solar panel is rotated away from the satellite body, so that the at least one solar panel is pointed towards the Sun, and the at least one splash plate reflector is rotated away from the satellite body to direct the radio frequency signals between the Earth and the at least one antenna.

21. A method, comprising:

stacking at least one satellite within a payload fairing of a launch vehicle, wherein:

the at least one satellite having a plurality of sections that are attached to each other, wherein the plurality of sections are folded or rotated together prior to launch, and the plurality of sections are unfolded or rotated away from each other when deployed upon reaching orbit;

a first one of the plurality of sections is a satellite body that includes at least one antenna;

a second one of the plurality of sections includes at least one solar panel attached to the satellite body for converting light from the Sun to electricity; and

a third one of the plurality of sections includes at least one splash plate reflector attached to the satellite body for reflecting radio frequency signals between Earth and the at least one antenna;

launching the at least one satellite into orbit using the launch vehicle; and

dispensing the at least one satellite from the payload fairing of the launch vehicle upon reaching orbit, such that, when the at least one satellite is deployed, the second one of the plurality of sections is rotated away from the first one of the plurality of sections so that the at least one solar panel is pointed towards the Sun, and the third one of the plurality of sections is rotated away from the first one of the plurality of sections so that the at least one splash plate reflector directs the radio frequency signals between Earth and the at least one antenna.

22. The method of claim 21 , wherein the at least one satellite comprises a plurality of satellites configured for being stacked within the payload fairing of the launch vehicle.

23. The method of claim 22 , wherein the plurality of satellites are disposed within the payload fairing of the launch vehicle in a stacked column configuration prior to launch.

24. The method of claim 22 , wherein the plurality of satellites comprises at least one top satellite disposed vertically on top of at least one bottom satellite within the payload fairing of the launch vehicle, and each bottom satellite includes a plurality of corner fittings that bear launch loads for the bottom satellite and the at least one top satellite.

25. The method of claim 22 , wherein the plurality of satellites are passively dispensed from the payload fairing of the launch vehicle upon reaching orbit.